CAJ | 학술논문

固化降温过程是固体火箭发动机装药制造过程中的一个重要环节，固化降温过程中各界面热应力的产生将直接影响装药性能，为此建立了装药数学模型和物理模型。基于粘弹性积分型本构关系，应用有限元分析软件，数值模拟固体火箭发动机装药的固化降温过程，得到固体推进剂在固化降温过程中应力、应变的变化规律。仿真结果对分析装药固化降温过程中的结构完整性有很好的参考价值。
고화강온과정시고체화전발동궤장약제조과정중적일개중요배절，고화강온과정중각계면열응력적산생장직접영향장약성능，위차건립료장약수학모형화물리모형。기우점탄성적분형본구관계，응용유한원분석연건，수치모의고체화전발동궤장약적고화강온과정，득도고체추진제재고화강온과정중응력、응변적변화규률。방진결과대분석장약고화강온과정중적결구완정성유흔호적삼고개치。
Cooling process after curing is a very pivotal step during manufacturing the SRM’s grain, and the thermal stress of different interface can affect directly the mechanical capability of the solid rocket motor’s grain. Mathematics and physical models of the grain were built up. Based on the viscoelastic integral constitutive relation, the cooling process after curing of the SRM’s grain was simulated by using the finite element software. The variation regulation of the equivalent stress and strain was obtained. The result has a good reference value in analyzing the construction of the SRM’s grain during cooling process after curing.